AD 2002-14-14

[Federal Register Volume 67, Number 139 (Friday, July 19, 2002)]
[Rules and Regulations]
[Pages 47656-47658]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 02-17533]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2001-NM-159-AD; Amendment 39-12814; AD 2002-14-14]
RIN 2120-AA64


Airworthiness Directives; McDonnell Douglas Model MD-11 and -11F 
Airplanes Equipped With General Electric Tail Engine Buildup Units 
(EBU)

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain McDonnell Douglas Model MD-11 and -11F airplanes 
that requires installation of a new support bracket with a clamp and 
screw to support the wire harness of the integrated drive generator 
(IDG). This action is necessary to prevent chafing and arcing of the 
wire harness of the IDG due to inadequate support, which could result 
in smoke and/or fire in the area of the forward engine mount. This 
action is intended to address the identified unsafe condition.

DATES: Effective August 23, 2002.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of August 23, 2002.

ADDRESSES: The service information referenced in this AD may be 
obtained from Boeing Commercial Aircraft Group, Long Beach Division, 
3855 Lakewood Boulevard, Long Beach, California 90846, Attention: Data 
and Service Management, Dept. C1-L5A (D800-0024). This information may 
be examined at the Federal Aviation Administration (FAA), Transport 
Airplane Directorate, Rules Docket, 1601 Lind Avenue, SW., Renton, 
Washington; or at the FAA, Los Angeles Aircraft Certification Office, 
3960 Paramount Boulevard, Lakewood, California; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, Washington, 
DC.

FOR FURTHER INFORMATION CONTACT: Technical Information: Brett Portwood, 
Aerospace Engineer, Systems and Equipment Branch, ANM-130L, FAA, Los 
Angeles Aircraft Certification Office, 3960 Paramount Boulevard, 
Lakewood, California 90712-4137; telephone (562) 627-5350; fax (562) 
627-5210.

[[Page 47657]]

    Other Information: Sandi Carli, Airworthiness Directive Technical 
Writer/Editor; telephone (425) 687-4243, fax (425) 227-1232. Questions 
or comments may also be sent via the Internet using the following 
address: <a href="/cdn-cgi/l/email-protection#eb988a858f82c5888a998782ab8d8a8ac58c849d"><span class="__cf_email__" data-cfemail="97e4f6f9f3feb9f4f6e5fbfed7f1f6f6b9f0f8e1">[email&#160;protected]</span></a>. Questions or comments sent via the 
Internet as attached electronic files must be formatted in Microsoft 
Word 97 for Windows or ASCII text.

SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
Aviation Regulations (14 CFR part 39) to include an airworthiness 
directive (AD) that is applicable to certain McDonnell Douglas Model 
MD-11 and -11F airplanes was published in the Federal Register on 
October 5, 2001 (66 FR 50872). That action proposed to require 
installation of a new support bracket with a clamp and screw to support 
the wire harness of the integrated drive generator (IDG).

Comments

    Interested persons have been afforded an opportunity to participate 
in the making of this amendment. Due consideration has been given to 
the single comment received.
    The commenter supports the proposed AD.

Explanation of Change to Applicability

    The FAA finds that Model MD-11F airplanes were not specifically 
identified by model name in the applicability of the proposed AD. 
However, those airplanes were identified by manufacturer's fuselage 
numbers in the effectivity listing of Boeing Alert Service Bulletin 
MD11-24A095, Revision 01, dated March 16, 2001, which was referenced in 
the applicability of the proposed AD. Therefore, we have revised this 
AD to specifically reference Model MD-11 and -11F airplanes where 
appropriate. In addition, we have revised the applicability of the 
existing AD to identify model designations as published in the most 
recent type certificate data sheet for the affected models and to 
specifically identify that the affected airplanes are equipped with 
General Electric tail engine buildup units (EBU).

Conclusion

    After careful review of the available data, including the comments 
noted above, the FAA has determined that air safety and the public 
interest require the adoption of the rule with the changes previously 
described. The FAA has determined that these changes will neither 
increase the economic burden on any operator nor increase the scope of 
the AD.

Cost Impact

    There are approximately 195 Model MD-11 and -11F airplanes of the 
affected design in the worldwide fleet. The FAA estimates that 67 
airplanes of U.S. registry will be affected by this AD, that it will 
take approximately 1 work hour per airplane to accomplish the required 
actions, and that the average labor rate is $60 per work hour. Required 
parts will be provided by Rohr, Inc., at no cost to the operators. 
Based on these figures, the cost impact of the AD on U.S. operators is 
estimated to be $4,020, or $60 per airplane.
    The cost impact figure discussed above is based on assumptions that 
no operator has yet accomplished any of the requirements of this AD 
action, and that no operator would accomplish those actions in the 
future if this AD were not adopted. The cost impact figures discussed 
in AD rulemaking actions represent only the time necessary to perform 
the specific actions actually required by the AD. These figures 
typically do not include incidental costs, such as the time required to 
gain access and close up, planning time, or time necessitated by other 
administrative actions.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect on the States, on the relationship between the national 
Government and the States, or on the distribution of power and 
responsibilities among the various levels of government. Therefore, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    For the reasons discussed above, I certify that this action (1) is 
not a ``significant regulatory action'' under Executive Order 12866; 
(2) is not a ``significant rule'' under DOT Regulatory Policies and 
Procedures (44 FR 11034, February 26, 1979); and (3) will not have a 
significant economic impact, positive or negative, on a substantial 
number of small entities under the criteria of the Regulatory 
Flexibility Act. A final evaluation has been prepared for this action 
and it is contained in the Rules Docket. A copy of it may be obtained 
from the Rules Docket at the location provided under the caption 
ADDRESSES.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, pursuant to the authority delegated to me by the 
Administrator, the Federal Aviation Administration amends part 39 of 
the Federal Aviation Regulations (14 CFR part 39) as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

2002-14-14  McDonnell Douglas: Amendment 39-12814. Docket 2001-NM-
159-AD.

    Applicability: Model MD-11 and -11F airplanes equipped with 
General Electric tail engine buildup units (EBU), as listed in 
Boeing Alert Service Bulletin MD11-24A095, Revision 01, dated March 
16, 2001; certificated in any category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
modified, altered, or repaired in the area subject to the 
requirements of this AD. For airplanes that have been modified, 
altered, or repaired so that the performance of the requirements of 
this AD is affected, the owner/operator must request approval for an 
alternative method of compliance in accordance with paragraph (b) of 
this AD. The request should include an assessment of the effect of 
the modification, alteration, or repair on the unsafe condition 
addressed by this AD; and, if the unsafe condition has not been 
eliminated, the request should include specific proposed actions to 
address it.

    Compliance: Required as indicated, unless accomplished 
previously.
    To prevent chafing and arcing of the wire harness of the 
integrated drive generator (IDG) due to inadequate support, which 
could result in smoke and/or fire in the area of the forward engine 
mount, accomplish the following:

Installation of New Support Bracket

    (a) Within 1 year after the effective date of this AD, install a 
new support bracket with a clamp and screw to support the wire 
harness of the IDG, per Boeing Alert Service Bulletin MD11-24A095, 
Revision 01, dated March 16, 2001.

    Note 2: Accomplishment of the installation per McDonnell Douglas 
Service Bulletin MD11-24-095, dated January 29, 1996, before the 
effective date of this AD, is considered acceptable for compliance 
with the requirements of paragraph (a) of this AD.

Alternative Methods of Compliance

    (b) An alternative method of compliance or adjustment of the 
compliance time that provides an acceptable level of safety may be

[[Page 47658]]

used if approved by the Manager, Los Angeles Aircraft Certification 
Office (ACO), FAA. Operators shall submit their requests through an 
appropriate FAA Principal Maintenance Inspector, who may add 
comments and then send it to the Manager, Los Angeles ACO.

    Note 3: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the Los Angeles ACO.

Special Flight Permits

    (c) Special flight permits may be issued in accordance with 
sections 21.197 and 21.199 of the Federal Aviation Regulations (14 
CFR 21.197 and 21.199) to operate the airplane to a location where 
the requirements of this AD can be accomplished.

Incorporation by Reference

    (d) The installation shall be done in accordance with Boeing 
Alert Service Bulletin MD11-24A095, Revision 01, dated March 16, 
2001. This incorporation by reference was approved by the Director 
of the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR 
part 51. Copies may be obtained from Boeing Commercial Aircraft 
Group, Long Beach Division, 3855 Lakewood Boulevard, Long Beach, 
California 90846, Attention: Data and Service Management, Dept. C1-
L5A (D800-0024). Copies may be inspected at the FAA, Transport 
Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington; or 
at the FAA, Los Angeles Aircraft Certification Office, 3960 
Paramount Boulevard, Lakewood, California; or at the Office of the 
Federal Register, 800 North Capitol Street, NW., suite 700, 
Washington, DC.

Effective Date

    (e) This amendment becomes effective on August 23, 2002.

    Issued in Renton, Washington, on July 2, 2002.
Jeffrey E. Duven,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 02-17533 Filed 7-18-02; 8:45 am]
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